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Abstract
A numerical investigation has been undertaken to evaluate the potential of tandem blades in improving the overall performance range of transonic compressors. A tandem rotor design with same inflow characteristics of the reference transonic rotor {u2018}NASA Rotor 37{u2019} is proposed. 2D CFD parametric study is first performed at the rotor mid-span section. Then, selected 3D tandem rotors are constructed from the best performing 2D tandem cascades. The best performing tandem design achieved 17% increase in the total pressure ratio with 2% improvement in the rotor adiabatic efficiency over the baseline {u2018}NASA Rotor 37